Advanced aerodynamic prediction software for versatile canard-controlled missile configurations

The present research is aimed at the development of advanced aerodynamic prediction software for canard-controlled missile to handle versatile configurations. The prediction code has been developed for aerodynamic prediction for missile configurations based on analytical techniques and empirical relations. An equivalent angle of attack methodology has been used for the estimation of nonlinear behavior in aerodynamics. The code has the capability to handle arbitrary roll orientation including the interdigitated tail, dual control, and angle of attack up to 90°. Four papers were identified as references for validating the prediction method after a thorough review of the literature. The geometrical parameters of the missile from the reference paper are extracted and given as input to the prediction code to find the aerodynamic characteristics. The obtained data from the prediction code are compared with the experimental data from the reference paper. For all the cases, the basic characteristics have excellent validation. In most cases, the prediction deviation is within 1.0d on the longitudinal stability and within 15% of the normal force coefficient. There is a 20% difference in the tail control characteristics. The deviation in tail control effectiveness is within 20%. The deviation for canard control is within 30% and is primarily caused by the interaction of the canard vortex with the tail.